Aerodynamic Loss and Mixing Over a Cavity Flame Holder Located Downstream of Pylon-aided Fuel Injection PDF Download
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Author: Lane C. Haubelt
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 306
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Book Description
Author: Lane C. Haubelt
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 306
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 13
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Book Description
An investigation of the nonreacting flow associated with pylon-aided gaseous fuel injection into a Mach 2 crossflow is described. In this study, a small pylon was positioned just upstream of a circular flush-wall fuel injector. Three pylon geometries were studied, along with a no-pylon reference case. In all cases, a typical cavity-based flameholder was positioned downstream of the fuel injector. The injectant plume characteristics were interrogated using a variety of laser-based and probe-based measurement techniques. Planar laser-induced fluorescence of nitric oxide was used to study the instantaneous plume structure. Spontaneous vibrational Raman scattering provided time-averaged plume characteristics and mixing information. Probe-based instrumentation was used in conjunction with the mixing data to estimate the total pressure losses associated with each configuration. Each pylon had a unique influence on the fuel-injection plume. In all cases, the presence of the pylon resulted in improved fuel penetration into the supersonic crossflow without significantly changing the total pressure-loss characteristics. Mixing efficiencies of the pylon-aided injection cases were not substantially different from the reference case.
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 666
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Author: Mitchell R. Pohlman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 246
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Author: William H. Allen (Jr.)
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 178
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Author: National Aeronaut Administration (Nasa)
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
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Book Description
Requirements to limit pollutant emissions from the gas turbine engines for the future High-Speed Civil Transport (HSCT) have led to consideration of various low-emission combustor concepts. One such concept is the Integrated Mixer-Flame Holder (IMFH). This report describes a series of IMFH analyses performed with KIVA-II, a multi-dimensional CFD code for problems involving sprays, turbulence, and combustion. To meet the needs of this study, KIVA-II's boundary condition and chemistry treatments are modified. The study itself examines the relationships between fuel vaporization, fuel-air mixing, and combustion. Parameters being considered include: mixer tube diameter, mixer tube length, mixer tube geometry (converging-diverging versus straight walls), air inlet velocity, air inlet swirl angle, secondary air injection (dilution holes), fuel injection velocity, fuel injection angle, number of fuel injection ports, fuel spray cone angle, and fuel droplet size. Cases are run with and without combustion to examine the variations in fuel-air mixing and potential for flashback due to the above parameters. The degree of fuel-air mixing is judged by comparing average, minimum, and maximum fuel/air ratios at the exit of the mixer tube, while flame stability is monitored by following the location of the flame front as the solution progresses from ignition to steady state. Results indicate that fuel-air mixing can be enhanced by a variety of means, the best being a combination of air inlet swirl and a converging-diverging mixer tube geometry. With the IMFH configuration utilized in the present study, flashback becomes more common as the mixer tube diameter is increased and is instigated by disturbances associated with the dilution hole flow. Deur, J. M. and Cline, M. C. Glenn Research Center NASA/CR-2004-213116, E-14610 NAS3-27235; WBS 714-09-46 GAS TURBINE ENGINES; FLAME HOLDERS; VAPORIZING; COMBUSTION; COMPUTATIONAL FLUID DYNAMICS; MIXERS; FUEL INJECTION; CONVERGENT-DIVERGENT NOZZLES; COMBUSTION CHAMBERS; FLAME PROPAGATION; FUEL SPRAYS; SECONDARY INJECTION
Author:
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Category :
Languages : en
Pages : 0
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This report describes the results of a recent series of experiments designed to examine the fundamental behavior of several cavity-based flameholder candidates in a non-reacting supersonic flow. Seven geometries were tested in conjunction with a new facility nozzle. Results indicate that the cavity aft ramp plays a strong role in determining the character of the shear layer which spans the length of the cavity. For rectangular cavities, a compression wave forms as the flow separates from the upstream corner of the cavity. Thus, the pressure on the upstream face increases above the freestream value. In these cases, the recompression which occurs at the aft wall is very sharp with strong pressure gradients at the axial location corresponding to the aft wall. These cases are also visibly unsteady. Reductions in the ramp angle yield more stable, two-dimensional flowfields. However, the character of the separation wave changes gradually from compressive to expansive as the ramp angle is reduced. As such, the shear layer tends to dip into the cavity and the recompression occurs more gradually as the shear layer reattaches to the aft wall. Changes in cavity offset ratio result in more dramatic changes in the cavity flowfield. The separation wave becomes strongly expansive leading to severe shear layer intrusion into the cavity. Aft wall changes do not strongly impact the character of the shear layer, although stability is enhanced and recompression is more gradual for shallower ramp angles.
Author: K.-Y. Hsu
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Kiran Hamilton Jeffrey Dellimore
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Corin Segal
Publisher: Cambridge University Press
ISBN: 0521838150
Category : Technology & Engineering
Languages : en
Pages : 271
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Book Description
Demand for high-speed propulsion has renewed development of the supersonic combustion ramjet engine (Scramjet engine) for hypersonic flight applications.
